CN100532200C - High-pressure steam dynamic sealing ejection machine for aircraft carrier - Google Patents
High-pressure steam dynamic sealing ejection machine for aircraft carrier Download PDFInfo
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- CN100532200C CN100532200C CNB2007100980298A CN200710098029A CN100532200C CN 100532200 C CN100532200 C CN 100532200C CN B2007100980298 A CNB2007100980298 A CN B2007100980298A CN 200710098029 A CN200710098029 A CN 200710098029A CN 100532200 C CN100532200 C CN 100532200C
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- ejection
- pressure steam
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Abstract
A high-pressure steam dynamic seal ejection machine is used for aircraft carrier, which includes a long-pipe-shape ejection cylinder, an ejection cylinder hatch disposed on the ejection cylinder, an ejection piston and a transmission arm. Cylinder walls of two sides of the ejection cylinder hatch are separately equipped with a seal cavity which is fixed on the ejection cylinder walls or integrated with the ejection cylinder walls; seal strips are arranged in the seal cavities and prevent high pressure steam in the ejection cylinder from escaping through the ejection cylinder hatch; the ejection piston is disposed in the ejection cylinder and outside diameter of the ejection piston matches to inside diameter of the ejection cylinder; a seal knife is arranged on the ejection piston, a transmission arm is disposed on upper of the seal knife, or the ejection piston, the seal knife and the transmission arm are integral structure; and the seal knife drills through the left and right seal strips. The invention can resolve seal problem of ejection machine during ejecting process.
Description
Technical field
The present invention relates to a kind of ejection machine of aircraft carrier, especially relate to a kind of high-pressure steam dynamic sealing ejection machine that is used for aircraft carrier.
Background technology
In August nineteen fifty, Britain has installed in the world the BXS-1 type steam ejector experiment of 45.5 meters of first power strokes and has succeedd on " Perseus " aircraft carrier deck.United States Navy has bought its patent and it is full-fledged the most at last, long 76.3 meters of the C-13-1 type steam ejector of the U.S., per minute can launch 2 fighter planes, the U.S. is developing later-model electromagnetic launch mode now, but be difficult to drop into practical at no distant date, the U.S. one aircraft carrier engineer points out at the plan of navy development electromagnetic launch device, " the steam ejector has high reliability; up to now; do not have airplane fault because of device proper in nearly ten million time catapult-assisted take-off to meet accident " meaning between the lines is to suspect the reliability of electromagnetic launch device, but has illustrated from the side that also the steam ejector is unusual failure-free.
Russia is in former Soviet Union period, just made aircraft carrier, what but aircraft carrier adopted is that the sliding formula of jumping is taken off, ejector is not installed, as a scientific and technological power, except information techenology falls behind, no matter be aeronautical and space technology, still other aspects all are the countries that is only second to the U.S., are difficult to the imagination and are rebuffed in front at the ejector that a western countries naval used more than 30 year.
It is the direction that China naval develops in the future to a certain extent that China builds aircraft carrier voluntarily.From world wide, make a strong aircraft-carrier battle group and be have challenging.Indispensable steam ejector on the aircraft carrier, carrier-borne aircraft, check cable, large-scale elevator, and technology such as high-output engine all grasp in America and Europe and even the U.S.'s one tame hand, this is a thing of never doing to Chinese Navy, and also can not have any country to sell the great technology research project of China abroad.
At the mode of taking off of carrier-borne aircraft, catapult-assisted take-off flies to compare with sliding jumping up, the catapult-assisted take-off large-scale early warning plane that can take off, and heavy weight fighter can be expired oily high gross weight takeoff; Because of catapult-assisted take-off can reduce the oil consumption of taking off, thereby early warning range and combat radius have been increased.The large-scale early warning plane that can not take off but the sliding formula of jumping is taken off, and since heavy weight fighter when taking off bullet-loading capacity and fuel load be restricted, consumption of fuel is big when taking off, thereby has influenced fighting effect greatly.
Chinese Navy is following builds the problem that aircraft carrier need solve ejector, solves and handles well if this problem Chinese Navy is not made great efforts, and that is petty, and he will directly influence the progress of following aircraft carrier construction and the establishing an army the time of Chinese Navy blue-water capable fleet of Chinese Navy.
The steam ejector is one of visual plant of large-scale through type aircraft carrier, and an ejector per minute can launch two carrier-borne aircrafts.The steam ejector is made up of external equipment and ejection machine and control system, and outer periphery has: devices such as desalting plant, hydraulic accumulator, high-pressure hydraulic pump, high-pressure pump, high pressure tank, ventilation flue, mould degree operated pneumatic valve, safety valve, ejection valve, gas line and boiler.Ejection machine has: open cylinder, piston, sealing arrangement, sealing cutter, transmission arm, tow rope, reciprocal cable wire, dead sheave, directive slide track etc.Control system has: pressure sensor, temperature sensor, position transduser and computer system etc. constitute complete ejector system.It relates to a lot of technology, metal smelt technology, metalworking technology, welding technique, computer software control technology and field engineering etc.Require from design to installation all very high, and the steam ejector adopts be " open cylinder " maximum difficult point be piston in the open cylinder motion, the sealing problem of sealing cutter during through opening.Because the kinetic energy of piston outwards transmits by the sealing cutter, seal cutter so certain width and length will be arranged, to satisfy its powerful propelling thrust, sealing cutter width has increased, owing to must back down sealing band at opening part during sealing cutter process open cylinder, if the big more sealing of the sealing intensity of sealing band is good more, the resistance that petty sealing cutter is subjected to is just big more, and the wearing and tearing of sealing band are also fast more.For addressing this problem is purpose of the present invention.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of high-pressure steam dynamic sealing ejection machine that is used for aircraft carrier.This launches function and solves the sealing problem that launches cylinder.
For solving the problems of the technologies described above, the present invention adopts following technical scheme: it comprise elongated tubular launch cylinder, be arranged on launch cylinder top launch cylinder openings, ejection piston and transmission arm;
Respectively be provided with an annular seal space on the described cylinder wall that launches the cylinder openings both sides, sealing chamber wall be fixed on launch on the cylinder wall or with launch cylinder wall and be structure as a whole; Be inlaid with sealing band in the described annular seal space, the sealing band of the right and left plays and stops the HCS that launches in the cylinder from launching the effect that cylinder openings is escaped;
Described ejection piston is located at and launches in the cylinder, its external diameter with launch cylinder bore and be complementary; Described ejection piston top sets firmly the sealing cutter, and the top of sealing cutter sets firmly transmission arm, or described ejection piston, sealing cutter and transmission arm are structure as a whole; Described sealing cutter passes the sealing band of the right and left.
Further, for saving material, described ejection piston is the bullet shaped of hollow; Bearing surface is made as the plane, has increased stressed area; The termination of advancing is made as taper, reduces air resistance.
Further,,, can make sealing band under the impact of launching cylinder inner high voltage steam so described sealing band inside is provided with many longitudinal stress reinforcing members because sealing band easy deformation when being subjected to impacting with high pressure makes it lose sealing function, vertically indeformable.
Further, for preventing sealing band when sealing, the HCS in the cylinder is upwards dug sealing band, leaks steam; The sealing surface of described sealing band is provided with the serration groove, makes it increase contact surface, and two sealing bands are interacted.
Further, for preventing annular seal space inner vapor gas blowby, the bearing surface of described sealing band is provided with raised line; The seal face of described sealing band and annular seal space is provided with halfpace.
Further, pile up for prevent that sealing band from producing in the process of sealing cutter motion, the two ends of described sealing band are provided with and are fixed on the tension fastener that launches the cylinder front and back ends, and this tension fastener can be fixed on the forward and backward two ends of sealing band cylinder opening beginning, end.
Further, enter in the cylinder for having prevented dust, the described cylinder openings top of launching is provided with dustproof seat, dust boot and dustproof elastic sealing gasket; Described dustproof seat is fixed on the upper outside of annular seal space, and described dust boot is fixed on the dustproof seat; Described dustproof elastic sealing gasket is located at the both sides up and down of transmission arm, enters from the slit of transmission arm both sides to prevent dust.
The present invention can solve the sealing problem of ejection machine in ejection process.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is that A-A along Fig. 1 is to cross-sectional schematic;
Fig. 3 is that the present invention removes behind the dust boot B-B along Fig. 1 to cross-sectional schematic;
Fig. 4 is a sealing band schematic top plan view of the present invention;
Fig. 5 is that C-C along Fig. 4 is to cross-sectional schematic;
Fig. 6 is that ejection piston of the present invention, sealing cutter and transmission arm connection structure are along Fig. 1 lateral observation scheme drawing.
Mark among the described figure is described below: 1-launches cylinder wall 2-and launches the dustproof elastic seal 13-sealing band longitudinal stress reinforcing member 14-of a cylinder 3-cylinder openings 4-ejection piston 5-sealing cutter 6-transmission arm 7-capsule walls 8-annular seal space 9-sealing band 10-dustproof seat 11-dust boot 12-and be sealed into steam pipe road 15-sealing band tension fastener 16-serration groove 17-raised line 18-boss
The specific embodiment
Referring to shown in Figure 1, the present invention includes elongated tubular launch cylinder 2, be arranged on launch cylinder 2 tops launch cylinder openings 3, ejection piston 4 and transmission arm 6;
Respectively be provided with an annular seal space 8 on the described cylinder wall 1 that launches cylinder openings 3 both sides, sealing chamber wall 7 with launch cylinder wall 1 and be structure as a whole; Be inlaid with sealing band 9 in the described annular seal space 8, the sealing band 9 of the right and left plays and stops the HCS that launches in the cylinder 2 from launching the effect that cylinder openings 3 is escaped; Described ejection piston 4 is located at and launches in the cylinder 2, its external diameter with launch cylinder 2 internal diameters and be complementary, slip before and after piston is can be during launching cylinder 2 free; Described ejection piston 4 tops set firmly sealing cutter 5, and the top of sealing cutter 5 sets firmly transmission arm 6, or described ejection piston 4, sealing cutter 5 and transmission arm 6 are structure as a whole; Described sealing cutter 5 passes the sealing band 9 of the right and left.
Further improved embodiment, described ejection piston 4 is the bullet shaped of hollow, has reduced the weight of ejection piston 4 like this, makes it that bigger acceleration/accel be arranged when being subjected to vapor pressure; Bearing surface is made as the plane, has increased stressed area; The termination of advancing is made as taper, reduces air resistance.
Further more improved embodiment, because sealing band 9 easy deformation when being subjected to impacting with high pressure makes it lose sealing function, so be provided with many longitudinal stress reinforcing members 13 in described sealing band 9 inside, can make sealing band 9 under the impact of launching cylinder 2 inner high voltage steams, vertically indeformable.
Further again improved embodiment, for preventing sealing band 9 when sealing, the HCSs that cylinder launches in 2 are upwards dug sealing band 9, leak steam; The sealing surface of described sealing band 9 is provided with serration groove 16, makes it increase contact surface, and two sealing bands are interacted.
Further again improved embodiment, for preventing annular seal space 8 inner vapor gas blowbies, the bearing surface that described sealing band 9 bears HCS is provided with raised line 17, and the seal face of described sealing band 9 and annular seal space 8 is provided with halfpace 18.
Further again improved embodiment, pile up for prevent that sealing band 9 from producing in the process of sealing cutter 5 motions, the two ends of described sealing band 9 are provided with tension fastener 15, and this tension fastener 15 can be fixed on beginning, the end that launches cylinder opening 3 with sealing band 9 forward and backward two ends.
Further, launch in the cylinder 2 for having prevented that dust from entering, described cylinder openings 3 tops of launching are provided with dustproof seat 10, dust boot 11 and dustproof elastic sealing gasket 12; Described dustproof seat 10 is fixed on the upper outside of annular seal space 8, and described dust boot 11 is fixed on the dustproof seat 10; Described dustproof elastic sealing gasket 12 is located at the both sides up and down of transmission arm 6, enters from the slit of transmission arm 6 both sides to prevent dust.
Dynamic seal (packing) principle of the present invention is as follows:
When launching preparation, progressively in launching cylinder 2, charge into HCS, ejection piston 4, sealing cutter 5 and transmission arm 6 are fixing above deck by " tow rope ", along with steam continue charge into, the pressure that launches in the cylinder 2 increases gradually, until to the pressure that launches that needs, also be full of HCS in the annular seal space 8 simultaneously.During the aircraft standby for takeoff, aviator's control " is led only buckle release ", tow rope is decontroled from the deck, the pressure that launches in the cylinder 2 all is discharged into (see figure 3) on ejection piston 4 bearing surfaces 41, ejection piston 4 high-speed motion in launching cylinder 2 (is seen Fig. 3, ejection piston 4 is at the direction high-speed motion of vertical paper among Fig. 1), drive sealing cutter 5, transmission arm 6 high-speed motion (seeing Fig. 1, Fig. 6) too, described transmission arm 6 promotes the aircrafts accelerated movement that shoots ahead; Sealing cutter 5 is in the process of motion, and the sealing band 9 on sealing cutter 5 afterbody both sides makes the rear portion of sealing cutter 5 be in sealing state owing to be subjected to the pressure of the HCS in the annular seal space 8 always; And the sealing band 9 of sealing cutter 5 front portions, owing to there is not the effect of sealed high pressure steam, so be in relaxed state always, whole process is along with the motion of ejection piston 4 is finished, just the same with the mode of operation of slide fastener, seal process also stops thereupon when ejection piston 4 stop motions, and seal process has stopped, but sealing state keeps.When once launch finish after, annular seal space 8 initial end blows off valve are opened, steam is discharged, sealing state finishes, at this moment whole sealing band 9 all is in relaxed state, when tow rope haul ejection piston 4, when sealing cutter 5 and transmission arm 6 turn back to and launch reference position, sealing cutter 5 is got back to the interior original position of annular seal space to sealing band 9 tops, and is ready for launching next time.In the middle of ejection piston 4 high-speed motions, postpone, launch cylinder 2 gas leakage in order to prevent sealing, between the bearing surface 41 of ejection piston 4 and the sealing cutter 5 distance is arranged, the possibility that the long more sealing of distance postpones gas leakage is just more little.
Claims (7)
1, a kind of high-pressure steam dynamic sealing ejection machine that is used for aircraft carrier, it comprise elongated tubular launch cylinder, be arranged on launch cylinder top launch cylinder openings, ejection piston and transmission arm; It is characterized in that:
Respectively be provided with an annular seal space on the described cylinder wall that launches the cylinder openings both sides, sealing chamber wall be fixed on launch on the cylinder wall or with launch cylinder wall and be structure as a whole; Be inlaid with sealing band in the described annular seal space, the sealing band of the right and left plays and stops the HCS that launches in the cylinder from launching the effect that cylinder openings is escaped;
Described ejection piston is located at and launches in the cylinder, its external diameter with launch cylinder bore and be complementary; Described ejection piston top sets firmly the sealing cutter, and the top of sealing cutter sets firmly transmission arm, or described ejection piston, sealing cutter and transmission arm are structure as a whole; Described sealing cutter passes the sealing band of the right and left.
2, high-pressure steam dynamic sealing ejection machine according to claim 1 is characterized in that: described ejection piston is the bullet shaped of hollow, and bearing surface is made as the plane, and the termination of advancing is made as taper.
3, high-pressure steam dynamic sealing ejection machine according to claim 1 is characterized in that: described sealing band inside is provided with many longitudinal stress reinforcing members.
4, according to claim 1 or 3 described high-pressure steam dynamic sealing ejection machines, it is characterized in that: the sealing surface of described sealing band is provided with the serration groove.
5, high-pressure steam dynamic sealing ejection machine according to claim 4 is characterized in that: the bearing surface that described sealing band bears HCS is provided with raised line, and the seal face of described sealing band and annular seal space is provided with halfpace.
6, high-pressure steam dynamic sealing ejection machine according to claim 5 is characterized in that: the two ends of described sealing band are provided with and are fixed on the tension fastener that launches the cylinder front and back ends.
7, high-pressure steam dynamic sealing ejection machine according to claim 5 is characterized in that: enter in the cylinder for having prevented dust, the described cylinder openings top of launching is provided with dustproof seat, dust boot and dustproof elastic sealing gasket; Described dustproof seat is fixed on the upper outside of annular seal space, and described dust boot is fixed on the dustproof seat; Described dustproof elastic sealing gasket is located at the both sides up and down of transmission arm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100980298A CN100532200C (en) | 2007-04-25 | 2007-04-25 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007100980298A CN100532200C (en) | 2007-04-25 | 2007-04-25 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101054115A CN101054115A (en) | 2007-10-17 |
| CN100532200C true CN100532200C (en) | 2009-08-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007100980298A Expired - Fee Related CN100532200C (en) | 2007-04-25 | 2007-04-25 | High-pressure steam dynamic sealing ejection machine for aircraft carrier |
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| Country | Link |
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| CN (1) | CN100532200C (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101708777B (en) * | 2009-11-17 | 2012-06-06 | 哈尔滨工程大学 | Pneumatic catapult |
| CN102485596A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft catapult of aircraft carrier |
| CN102485595A (en) * | 2009-11-24 | 2012-06-06 | 刘华 | Aircraft landing damper for aircraft carrier |
| CN102241276A (en) * | 2010-05-16 | 2011-11-16 | 罗云 | Steam ejection device |
| CN101865633A (en) * | 2010-06-04 | 2010-10-20 | 哈尔滨工程大学 | Dynamic tile sealing pneumatic ejection transmitter |
| CN102343981A (en) * | 2010-07-30 | 2012-02-08 | 杨建东 | Steam power catapult of aircraft carrier plane |
| CN102980439A (en) * | 2011-09-06 | 2013-03-20 | 罗云 | Rubber strip type steam ejection device |
| CN103185138B (en) * | 2011-12-29 | 2015-04-15 | 任明琪 | Sealing belt for opening steam cylinder of shipboard aircraft ejector |
| CN102745333A (en) * | 2012-07-31 | 2012-10-24 | 李文铎 | Internal combustion steam boosting take-off unit of airplane |
| CN103213688A (en) * | 2013-04-30 | 2013-07-24 | 张春平 | Shipboard aircraft ejector |
| CN103939611A (en) * | 2014-05-07 | 2014-07-23 | 夏彤宇 | Flexible opening fastening and sealing device of opening air cylinder |
| CN104443421A (en) * | 2014-07-29 | 2015-03-25 | 李广 | Pressure accumulating steam catapult with two spherical tanks and half-opening cylinder |
| CN105371699A (en) * | 2014-08-14 | 2016-03-02 | 李犁 | Energy gathering cannon |
| CN104773301B (en) * | 2015-03-19 | 2016-08-17 | 孟昭贵 | Carrier-borne aircraft steam catapult |
| CN105698001B (en) * | 2016-04-29 | 2018-07-06 | 杨文清 | A kind of aerodynamic energy aircraft catapult-launching gear |
-
2007
- 2007-04-25 CN CNB2007100980298A patent/CN100532200C/en not_active Expired - Fee Related
Non-Patent Citations (2)
| Title |
|---|
| 弹射器的"秘密". 远峰.舰载武器，第2005/03期. 2005 |
| 弹射器的"秘密". 远峰.舰载武器，第2005/03期. 2005 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101054115A (en) | 2007-10-17 |
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Granted publication date: 20090826 Termination date: 20100425 |